An Architecture for On-Line Measurement of the Tip Clearance and Time of Arrival of a Bladed Disk of an Aircraft Engine

Gil-García, José Miguel; Solís, Alejandro; Aranguren, Gerardo

doi:10.3390/s17102162

Cited by 23 publications

(13 citation statements)

References 23 publications

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“…As early as 1982, NASA and GE published their cooperative research results of an optical sensor for measuring tip clearance, including test results on the compressor disk [7]. Since 2013, García I. and Zubia J. et al from University of the Basque Country had been continuously published the results of optical method application in tip clearance measurement [8,9,10,11,12]. While, the study of Andreas K. et.al.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of High Temperature-Resistant Inductive Sensor for Blade Tip Clearance Measurement

Zhao

Liu

Lyu

et al. 2018

Sensors

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Turbine tip clearance of aero-engine is important to engine performance. Proper control of rotor tip clearance contributes to engine efficiency improvement and fuel consumption reduction. Therefore, accurate tip clearance measurement is essential. The inductive measurement method is one of the non-contact distance measurement methods, which has the characteristics of high sensitivity, fast response speed and strong anti-interference ability. Based on the principle of inductive sensor measuring tip clearance, the ambient temperature change will cause the material electromagnetic performance change for the conductivity and permeability varies with temperature. The calibration experiment was conducted to obtain the sensor resolution and sensing range. The effect of temperature on sensor parameters was extracted from high temperature experiment data. Results show the resolution of planar coil made of platinum wire can be 10 μm and the maximum sensing range can reach 5 mm. At temperature from 500 ℃ to 1100 ℃, coil inductance almost does not change with temperature while coil resistance varies exponentially with temperature, that means the coil inductance variation can reflect the tip clearance change and resistance can indicate the measuring temperature.

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Section: Introductionmentioning

confidence: 99%

Experimental Investigation of High Temperature-Resistant Inductive Sensor for Blade Tip Clearance Measurement

Zhao

Liu

Lyu

et al. 2018

Sensors

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“…The validation was carried out with the three sets of rotation speeds mentioned. The TC processed by the instrument differed from the value obtained by the PC processing less than 1.8% in the worst case [22]. Likewise, the optic sensor deviated a 2.2% in the worst case from the discharge sensor employed in the real tests [20].…”

Section: Resultsmentioning

confidence: 77%

Architecture for Measuring Blade Tip Clearance and Time of Arrival with Multiple Sensors in Airplane Engines

Gil-García

Aranguren

2018

International Journal of Aerospace Engineering

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The performance of airplane engines is influenced by the performance of their bladed disks. The loads those engines are under, both internal and external, are the origin of vibrations than can jeopardize their integrity. Traditionally, monitoring of those vibrations has been circumscribed to prototyping and quality tests of manufactured disks. However, the development of nonintrusive sensors and techniques to evaluate the vibration based on those sensors opens the monitoring of full engines, even onboard, to new possibilities. In order to assess the vibrations with these techniques, several sensors should be employed. The distance from the blade tip to the casing (tip clearance) and the time of arrival of a blade in front of the sensor are two parameters that are used as a starting point to characterize the vibrations. A flexible architecture to extract these parameters from the blades of a gas turbine has been developed. The generalization of this architecture is introduced which is able to deal with several sensors simultaneously. An implementation of this architecture has been carried out employing a trifurcated optic sensor, whose working principle is explained. A study of the resources required to implement this architecture on measurements of several optic sensors simultaneously and in parallel is presented. The architecture and measurement method have been validated using signals recorded during the test of the compressor stage with 146 blades on a turbine rig.

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“…This kind of a coarse measurement, known as Zablotskiy method [42], should, therefore, be used only as a first approximation, while reliable synchronous vibration measurement requires a multi-sensor system. This is extremely important as viewing displacement plots for blades provides very little information but is often considered by engineers as an essential tool e.g., [3,43,44].…”

Section: Eo2 Forced Responsementioning

confidence: 99%

Non-Contact Measurement of Blade Vibration in an Axial Compressor

Przysowa

Russhard²

2019

Sensors

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Complex blade responses such as a rotating stall or simultaneous resonances are common in modern engines and their observation can be a challenge even for state-of-the-art tip-timing systems and trained operators. This paper analyses forced vibrations of axial compressor blades, measured during the bench tests of the SO-3 turbojet. In relation to earlier studies conducted in Poland with a small number of sensors, a multichannel tip-timing system let us observe simultaneous responses or higher-order modes. To find possible symptoms of a failure, blade responses in a healthy and unhealthy engine configuration with an inlet blocker were studied. The used analysis methods covered all-blade spectrum and the circumferential fitting of blade deflections to the harmonic oscillator model. The Pearson coefficient of correlation between the measured and predicted tip deflection is calculated to evaluate fitting results. It helps to avoid common operator mistakes and misinterpreting the results. The proposed modal solver can track the vibration frequency and adjust the engine order on the fly. That way, synchronous and asynchronous vibrations are observed and analysed together with an extended variant of least squares. This approach saves a lot of work related to configuring the conventional tip-timing solver.

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An Architecture for On-Line Measurement of the Tip Clearance and Time of Arrival of a Bladed Disk of an Aircraft Engine

Cited by 23 publications

References 23 publications

Experimental Investigation of High Temperature-Resistant Inductive Sensor for Blade Tip Clearance Measurement

Experimental Investigation of High Temperature-Resistant Inductive Sensor for Blade Tip Clearance Measurement

Architecture for Measuring Blade Tip Clearance and Time of Arrival with Multiple Sensors in Airplane Engines

Non-Contact Measurement of Blade Vibration in an Axial Compressor

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